Robust propellant liner and interfacial propellant burn rate con

Details Robust propellant liner and interfacial propellant burn rate con Robust propellant liner and interfacial propellant burn rate con

1995-05-24

1998-06-16

Gorr, Rachel

Synthetic resins or natural rubbers -- part of the class 520 ser

Synthetic resins

From reactant having at least one -n=c=x group as well as...

528 75, 525417, 524707, C08G 1816

Patent

active

057672210

ABSTRACT:
A robust polyurethane liner is disclosed for solid propellant rocket motors which is insensitive to large variations in stoichiometry, exhibits increased cohesive strength and, when used in combination with a unique two coat (wet coat) liner process described below, modifies the ballistic properties of the adjacent interfacial propellant layer. The liner compositions include a polymeric binder having a plurality of reactive hydroxyl functional groups and a curing agent having a plurality of reactive isocyanate functional groups. The quantity of binder and curing agent is selected such that the NCO/OH ratio is in the range from 1.5 to 4.5. Diisocyanate curing agents are particularly useful. A bonding agent, such as a polyfunctional aziridine compound, is typically present in the liner composition in an amount ranging from about 3% to about 5%, by weight. An oligomer catalyst is included in the liner composition in an amount ranging from about 15% to about 50%, by weight. Diammonium phosphate ((NH.sub.4).sub.2 HPO.sub.4) functions as an oligomer catalyst and as a ballistic modifier to inhibit propellant burn rate when the liner is cured concurrently with the propellant. A colorant, such as rhodamine B, may optionally be included to assist in determining coverage or thickness of the liner coating.

REFERENCES:
patent: 4009130 (1977-02-01), Zimmerman et al.
patent: 4187215 (1980-02-01), Wrightson
patent: 4331871 (1982-05-01), Allinikov
patent: 5273785 (1993-12-01), Sinclair et al.

Affiliated with

Also associated with

Rating

Robust propellant liner and interfacial propellant burn rate con does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Robust propellant liner and interfacial propellant burn rate con, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Robust propellant liner and interfacial propellant burn rate con will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-1726870